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    Remote control powered parafoil aircraft
    414.
    发明申请
    Remote control powered parafoil aircraft 审中-公开
    远程控制动力parafoil飞机

    公开(公告)号：US20020193914A1

    公开(公告)日：2002-12-19

    申请号：US10045777

    申请日：2002-01-11

    Inventor： Tony L. Talbert ,  John Mark Kulo

    IPC: B64C013/00

    CPC classification number: B64C13/50 ,  B64C31/036 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/08

    Abstract: A remote-control powered parafoil aircraft has an aircraft body (1) that is engine powered and hung with lines (2) from an air-expandable wing (3, 30). The lines include control lines (15) with which air flow and aerodynamic shape of the air-expandable wing are variable selectively from a foil controller (18, 19, 20) on the aircraft body for flight-mode control. Sight from a television camera (8) on the aircraft body is televised to a control unit (9) from which control data is transmitted selectively from proximate the control unit to the foil controller (14) with a multi-axis joystick or similar control, to an engine (6) on the parafoil body from an engine controller (24) and to an item servo (29) for control of optional items (45) on the aircraft body.

    Abstract translation: 遥控动力的parafoil飞机具有发动机动力并悬挂有来自可膨胀翼（3,30）的线（2）的飞机主体（1）。 这些管线包括控制线（15），空气膨胀翼的空气流动和空气动力学形状可选择性地从飞行器体上的箔控制器（18,19,20）可变地进行飞行模式控制。 来自飞机机体上的电视摄像机（8）的视线被电视传送到控制单元（9），控制数据通过多轴操纵杆或类似的控制从控制单元的附近被选择性地发送到箔片控制器（14） 从发动机控制器（24）到达副翼车体上的发动机（6）和用于控制飞机主体上的可选项（45）的物品伺服（29）。

    Vehicle refueling system
    415.
    发明授权
    Vehicle refueling system 失效
    车辆加油系统

    公开(公告)号：US6142421A

    公开(公告)日：2000-11-07

    申请号：US231368

    申请日：1999-01-13

    Applicant: Miles R. Palmer

    Inventor： Miles R. Palmer

    IPC: B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

    CPC classification number: B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

    Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

    Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

    Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors
    416.
    发明授权
    Snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
    用于转子组件的缓冲组件，其具有导管的同轴反转转子

    公开(公告)号：US5340279A

    公开(公告)日：1994-08-23

    申请号：US903063

    申请日：1992-06-22

    Applicant: James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

    Inventor： James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

    IPC: B64C27/10 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  B64C27/38

    CPC classification number: B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

    Abstract: A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub. The snubber assembly includes a spherical self-aligning bearing, a bearing bolt, a locking nut, a snubber bracket secured in combination with the spherical bearing, and securing bolts. The spherical bearing, snubber bracket combination is rotatably mounted within the bearing cavity utilizing the bearing bolt. The bearing bolt is secured in combination with the rotor hub utilizing the locking nut, which is threaded onto the bearing bolt in the internal cavity to jam against the inboard internal bulkhead. The securing bolts are utilized to secure the snubber bracket in combination with the corresponding integrated torque tube/spar member of the rotor assembly.

    Abstract translation: 一种用于转子组件的缓冲组件，其具有导管同轴的反向旋转转子，其设计优化以便于利用自对准轴承并安装在对应的挠性梁至转子轮毂附接接头的内侧，从而增强可接近性并减少维护 费用 转子组件的转子轮毂被设计为优化用于将缓冲器组件与其组合固定并且包括多个臂，每个臂形成用于将转子组件挠性束附接到转子毂的外侧U形夹。 在U形夹的内侧，每个转子轮毂臂包括具有穿过其中的螺栓孔的外侧内部隔板和具有穿过其中的螺栓孔的内侧内部隔板。 内侧和外侧的内部舱壁组合地限定了轴承腔和用于将缓冲器组件与转子毂组合固定的内部空腔。 缓冲组件包括球形自调心轴承，轴承螺栓，锁紧螺母，与球面轴承组合固定的缓冲支架和固定螺栓。 球轴承，缓冲支架组合使用轴承螺栓可旋转地安装在轴承腔内。 轴承螺栓利用锁定螺母与转子毂组合固定，该锁定螺母被拧到内部空腔中的轴承螺栓上以卡在内侧内部舱壁上。 紧固螺栓用于将缓冲支架与转子组件的相应的集成扭矩管/翼梁构件组合固定。

    Integrated spline/cone seat subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors
    417.
    发明授权
    Integrated spline/cone seat subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors 失效
    用于转子组件的集成花键/锥座组件，具有导管同轴的反转转子

    公开(公告)号：US5281099A

    公开(公告)日：1994-01-25

    申请号：US903064

    申请日：1992-06-22

    Applicant: David H. Hunter ,  Timothy A. Krauss ,  Vincent F. Millea

    Inventor： David H. Hunter ,  Timothy A. Krauss ,  Vincent F. Millea

    IPC: B64C11/02 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025 ,  Y10T403/7035

    Abstract: An integrated spline/cone seat subassembly for a rotor assembly that is design optimized to minimize the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies thereof. The integrated subassembly includes a rotor hub having a shaft aperture with a plurality of hub splines extend radially inwardly therefrom. The lower portion of each hub spline has an outwardly tapered portion that makes a predetermined angle with respect to the hub centerline. The integrated subassembly further includes a rotor shaft having a primary shaft portion of a first diameter, an end shaft portion having an intermediate second diameter less than the first diameter, and a conic transition portion that makes a predetermined angle with respect to the rotor shaft axis. The end shaft portion has a plurality of shaft splines extending radially outwardly therefrom that defines a third diameter that is equal to the first diameter. The hub and shaft splines are sized to accommodate the torque required by the rotor assembly and interleaved to provide a rotational interlock between the rotor hub and rotor shaft. The tapered portions of the hub splines abuttingly engage and are mechanically supported by the conic transition portion of the rotor shaft. The first diameter of the rotor shaft defines the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies of the rotor assembly.

    Abstract translation: 用于转子组件的集成花键/锥座组件，其设计优化以使转子轴，转子轴轴承，变速器壳体和其斜盘组件的径向尺寸最小化。 集成子组件包括具有轴孔的转子轮毂，其具有从其径向向内延伸的多个轮毂花键。 每个毂花键的下部具有相对于轮毂中心线形成预定角度的向外的锥形部分。 集成子组件还包括具有第一直径的主轴部分的转子轴，具有小于第一直径的中间第二直径的端轴部分和相对于转子轴轴线形成预定角度的圆锥过渡部分 。 端轴部分具有从其径向向外延伸的多个轴花键，其限定等于第一直径的第三直径。 轮毂和轴花键的尺寸适于容纳转子组件所需的扭矩并交错以在转子毂和转子轴之间提供旋转互锁。 轮毂花键的锥形部分邻接地接合并由转子轴的锥形过渡部分机械地支撑。 转子轴的第一直径限定了转子轴，转子轴承，变速器壳体和转子组件的斜盘组件的径向尺寸。

    REDUNDANCY IN UAV ENGINE TIMING POSITION SYSTEMS
    418.
    发明公开
    REDUNDANCY IN UAV ENGINE TIMING POSITION SYSTEMS 审中-公开

    公开(公告)号：EP3143269A4

    公开(公告)日：2018-02-21

    申请号：EP15812348

    申请日：2015-06-23

    Applicant: ORBITAL AUSTRALIA PTY LTD

    Inventor： UTLEY TYRON DEAN ,  BUTERS NICOLASS HARRY ,  NARAYAN JAYESH

    IPC: F02D41/22 ,  F02B77/08 ,  F02D41/00 ,  G01M15/06

    CPC classification number: F02D41/009 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/044 ,  F02D41/222 ,  F02D2200/101 ,  F02D2400/08 ,  H02K11/21 ,  Y02T10/40

    Abstract: Redundancy in engine timing position sensing maintains a UAV operational in the event of failure of a primary engine timing position sub-system. The redundancy avoids duplication of the primary crankshaft timing position sensing components, and avoids adding weight, cost and component complexity. Conditioned (square) waveform(s) (102) is/are created from respective sinusoidal waveform(s). Each consecutive leading edge (103a) and trailing edge (103b) of the pulses of the square waveform (102) is derived from the crossing of the zero voltage value by consecutive sinusoidal waveforms A,B,C (e.g. Voltage (V) vs Time (t) or angular degrees). The square pulse waveform (102) is output (104) to a microcontroller (106) to create and output a pseudo crankshaft timing position signal (108) to be used by an ECU to determine ignition and fuel injection events in the event that the primary timing signal from the crankshaft position sensor (CPS) has failed. The signal (108) output to the ECU can have a missing pulse (116) (i.e. indicative of a TDC position of the engine crankshaft) as well as multiple square pulses (114) corresponding to the pulses of the initial square pulse waveform (102). The waveform signal (108) is therefore derived from the alternator waveform signal(s) and provides a pseudo crankshaft timing position signal in the event of failure of the primary or initial CPS signal.

    AIRCRAFT HAVING A VERSATILE PROPULSION SYSTEM
    419.
    发明公开
    AIRCRAFT HAVING A VERSATILE PROPULSION SYSTEM 审中-公开
    飞机具有多功能推进系统

    公开(公告)号：EP3263456A1

    公开(公告)日：2018-01-03

    申请号：EP17179010.8

    申请日：2017-06-30

    Applicant: Bell Helicopter Textron Inc.

    Inventor： OLDROYD, Paul K ,  McCULLOUGH, John Richard

    IPC: B64C39/02 ,  B64C29/00 ,  B64D27/06 ,  B64D27/24 ,  B64D31/00 ,  B64D35/08 ,  B64D27/02 ,  B64D27/26

    CPC classification number: B64D27/12 ,  B64C11/46 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/086 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2211/00 ,  B64D27/06 ,  B64D27/24 ,  B64D27/26 ,  B64D31/00 ,  B64D35/08 ,  B64D2027/026 ,  B64D2027/262 ,  Y02T50/62

    Abstract: An aircraft (10) having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft (10) includes an airframe (12) and a versatile propulsion system attached to the airframe (12). The versatile propulsion system includes a plurality of propulsion assemblies (26a-d). A flight control system (40) is operable to independently control the propulsion assemblies (26a-d). The propulsion assemblies (26a-d) are interchangeably attachable to the airframe (12) such that the aircraft (10) has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies (26a-d) from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies (26a-d) from an electric power source.

    Abstract translation: 一种具有垂直起降战斗模式和向前飞行模式的飞机（10）。 飞机（10）包括机身（12）和附接到机身（12）的多功能推进系统。 多功能推进系统包括多个推进组件（26a-d）。 飞行控制系统（40）可操作以独立地控制推进组件（26a-d）。 推进组件（26a-d）可互换地附连到机身（12），使得飞机（10）具有液体燃料飞行模式和电动飞行模式。 在液体燃料飞行模式中，能量从液体燃料提供给每个推进组件（26a-d）。 在电动飞行模式中，能量从电源被提供给每个推进组件（26a-d）。

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